JPH04201694A - Spanwise blowing device for aircraft - Google Patents

Abstract

PURPOSE:To simplify the construction of an air blowing device and reduce the weight thereof by keeping continuity between an air intake on the lower side of a fuselage- wing blend section and an air blow hole at the side of the blend section in slidable contact with a leading flap, and opening the air blow hole for blowing the air in a wing width direction, when the leading flap is operated. CONSTITUTION:A main wing 4 outside a fuselage-wind blend section 3 at both sides of a fuselage 2, is constituted of a fixed wing 5, a trailing flap 6 at the trailing edge thereof and a maneuver flap 7 at the leading edge thereof. The maneuver flap 7 is pivotally supported in such a way that the end thereof can move vertically. In addition, both edges of the flap 7 are in slidable contact with the aforesaid blend section 3. An air intake 8 is provided on the lower side of the section 3, and an air blow hole 9 is provided on the section 3 where in slidable contact with the maneuver flap 7. In addition, the air intake 8 and air blow hole 9 are continuous to each other via an air duct 10. When the end of the maneuver flap 7 declines, the air blow hole 9 opens and becomes continuous to the air intake 8. Consequently, the air blows from the air blow hole 9 in a wing width direction, thereby strengthening a large separation eddy current generated on a main wing.

Description

Detailed Description of the Invention [Field of Industrial Application] The present invention relates to a spanwise blowing device for an aircraft. This invention relates to a spanwise blowing device for an aircraft, in which an air outlet is provided on the side surface of a wing-fuselage blend in sliding contact with the air intake, and the air intake and the air outlet are communicated by an air duct whose flow passage cross-sectional area gradually decreases toward the air outlet. .

[Conventional technology]

Generally, when an aircraft such as a fighter jet flies at a high angle of attack, a large separation vortex is generated on the upper surface of the wing, and the airflow overcomes this large separation vortex and flows back into contact with the surface of the wing, increasing the lift of the wing. maintain. However, when the angle of attack of the aircraft becomes larger than a certain value,
The large separation vortex collapses and the wing rapidly loses its lift.

FIG. 6 shows a large separation vortex generated on the upper surface of an aircraft wing. When the aircraft 15 flies at a high angle of attack, a large separation vortex Wl is generated on the upper surface of the wing 16. The large separation vortex W1 extends from the root of the blade 16 almost along the leading edge of the blade and reaches the tip of the blade 16. However, when the angle of attack of the aircraft 15 exceeds a certain value, the large separation vortex W1 collapses on the way without reaching the tip of the wing 16, as shown in the figure. When the large separation vortex W1 collapses, the airflow separates from the blade 16 and the lift of the blade 16 is lost.

To counter this, air jets are installed at the root of the wing using air bleed from the aircraft's engine compressor, and high-pressure air is jetted across the width of the wing, creating further vortex flow inside the large separation vortex. A spanwise blowing device is known in which the large separation vortices are reinforced by a large separation vortex, and even at a larger angle of attack, the large separation vortices are maintained so that the lift of the wing is not lost (Japanese Patent Publication No. 57-6).
No. 0200, JP-A-58-183388, N
ASA TN D-7907, AIAA-84-2
195).

FIG. 7 shows a separated vortex produced by a conventional spanwise blowing device.

An air outlet 17 is provided at the root of a wing 16 of an aircraft 15. This air jet port 17 is connected to a discharge pipe of a compressor of an engine (not shown), and is configured to jet compressed air from the compressor.

Further, a control valve for selectively closing and opening the pipe is provided in the pipe connecting the air outlet 17 and the compressor, and a control device for controlling this control valve is also provided.

When the aircraft 15 flies at a high angle of attack, a large separation vortex W1 is generated on the upper surface of the wing 16. In response to the generation of this large separation vortex Wl, the high pressure air of the compressor is ejected from the air ejection port 17 in the width direction of the blade. This high-pressure air is influenced by the airflow on the upper surface of the blade and generates a small separated vortex W2. Large separation vortex Wl is small separation vortex W
2, it does not collapse even at large angles of attack and extends to the tip of the wing to maintain the lift of the wing, as shown in the figure.

[Problem to be solved by the invention]

However, since conventional spanwise blowing devices utilize bleed air from the engine's compressor, there has been a problem in that the thrust of the engine is reduced.

Furthermore, unless the engine speed and the amount of oil are precisely controlled, there is a problem that the engine may stop due to the amount of oil being too large.

In addition, since a control valve and a control device must be provided to selectively control the ejection and stop of compressed air, the weight of the aircraft increases and the structure becomes complicated.

SUMMARY OF THE INVENTION An object of the present invention is to provide a spanwise blowing device for an aircraft that has a simple structure, is light in weight, and completely prevents engine stoppage accidents without impairing the thrust of the engine.

[Means to solve the problem]

To achieve the above object, the aircraft spanwise blowing device of the present invention has wing-fuselage blends on both sides of the fuselage, and has a main wing on the outside of each wing-fuselage blend, and is movable to the leading edge of the main wing. In an aircraft having a leading edge flap, an air intake port is provided on the lower surface of the wing-fuselage blend, and an air jet port is provided on the side surface of the wing-fuselage blend that makes sliding contact with the leading edge flap, and the air intake port and the air jet port are connected to each other. are connected to each other by an air duct, and the air outlet is closed by the side end surface of the leading edge flap when the leading edge flap is not operated, and is opened when the leading edge flap is operated, and is configured to blow out air in the widthwise direction of the wing. It is characterized by a snake.

[Effect]

The above spanwise blowing device for an aircraft according to the present invention includes an air intake port provided on the lower surface of the wing-fuselage blend where the air pressure increases during high angle of attack flight, and an air jet port provided on the side surface of the wing-fuselage blend where the air pressure becomes low. Since the air intake port and the air jet port are connected through an air duct, if the air jet port is opened during high angle of attack flight, air will flow out from the air jet port due to the difference in air pressure between the air intake port and the air jet port. A small advantage that ejects in the width direction of the wing and reinforces the large separation vortex! A vortex is formed.

Furthermore, the air outlet is configured so that it is closed by the side end face of the leading edge flap when the leading edge flap of wing No. 11 is not activated, and is opened when the leading edge flap is activated. In response to actuation of the leading edge flap to obtain high lift, air is ejected from the air outlet toward the midleaf. Therefore, there is no need for a control valve or a control device to control the operating timing of the spanwise blowing device.

〔Example〕

An embodiment of the present invention will be described below with reference to the accompanying drawings.

1 to 3 show a portion of an aircraft equipped with the spanwise blowing device of the present invention.

The aircraft, designated as a whole by the reference numeral 1, has a fuselage 2, on both sides thereof a wing-fuselage blend 3 integrally formed with the fuselage 2, and further has a main wing 4 outside the wing-fuselage blend 3. .

The main wing 4 is composed of a fixed wing 5, a trailing edge flap 6 at the trailing edge, and a maneuver flap 7 at the leading edge. The maneuver flap 7 is pivoted so that its tip can move up and down, and is in sliding contact with the wing-fuselage blend 3 at its side end surface.

An air intake port 8 is provided on the lower surface of the wing body blend 3, and an air jet port 9 is provided on the sliding surface with the maneuver flap 7.
is provided. The air intake port 8 and the air outlet 9 are communicated by an air duct 10 whose flow passage cross-sectional area gradually decreases toward the air outlet 9. ' Figure 4 shows the aircraft 1 in operation with the spanwise blowing device of the present invention.

When the aircraft 1 flies at a high angle of attack, the tip of the maneuver flap 7 is lowered and the camber of the main wing 4 is increased to increase the pressure difference between the upper and lower surfaces of the wing, thereby obtaining high lift. At this time, a large separation vortex V1 is generated from the leading edge of the root of the main wing 4, and the airflow overcomes this large separation vortex Vl and flows again in contact with the upper surface of the main wing 4, so that the lift of the main wing 4 is maintained. Furthermore, by lowering the tip of the maneuver flap 7, the air outlet 9 provided on the sliding contact surface between the wing fuselage blend 3 and the maneuver flap 7 is opened, and the air intake port 8 and the air outlet 9 are connected to the air duct 10. communication is established through the When the aircraft is flying at a high angle of attack, the pressure of the air on the lower surface of the wing-fuselage blend 3 is higher than that at the root of the wing, so air flows in from the air intake port 8.
The air is ejected from the air outlet 9 at high speed in the direction of application. The air ejected from the air outlet 9 becomes a small separated vortex v2 due to the influence of the airflow on the upper surface of the main wing 4. Small separation vortex V2 is large separation vortex v1
The large-separation vortex v2 is extended concentrically with respect to the large-separation vortex v2, and the large-separation vortex v2 is maintained even in a large attack angle range to maintain the lift of the wing.

Figure 5 shows the operating condition of the wing during cruising of the aircraft. When cruising at high speed, the aircraft 1 flies with the tip of the maneuver flap 7 raised so that the maneuver flap 7 and the fixed wing 5 are on the same plane. By holding the maneuver flaps 7 horizontally, the main wing 4 has low air resistance and lift, and has a shape suitable for high-speed cruising. During high-speed cruising, the large separated vortex is not generated on the upper surface of the main wing 4, and since the air outlet 9 is closed by the side end surface of the maneuver flap 7, the small separated vortex is not generated either.

〔Effect of the invention〕

As is clear from the above description, according to the present invention, the air intake of the spanwise blowing device is provided on the lower surface of the wing-body blend where the air pressure is high, and the air jet port is provided on the lower surface of the wing-body blend where the air pressure is low. Since it was installed on the side of
When flying at a high angle of attack with the maneuver flaps lowered, the difference in air pressure on the surface of the aircraft causes air to be ejected from the air outlet in the direction of the flight, reinforcing the large separation vortices that have formed on the upper surface of the main wing. Since the bolt of the engine compressor is not used as an air flow to reinforce the large M vortex, it is possible to completely prevent the engine thrust from being reduced by the bolt of the compressor or the engine to stop.

Furthermore, the spanwise blowing device of the present invention connects the air intake port and the air jet port with an air duct, and is configured so that air is jetted out by lowering the manifold bar flap during high lift. Therefore, it is possible to obtain a spanwise blowing device that does not require a control valve or a control device for controlling the ejection or stopping of air, and is extremely simple in structure and lightweight.

[Brief explanation of the drawing]

FIG. 1 is a plan view showing a part of an aircraft having an embodiment of the spanwise blowing device of the present invention, and FIG. 2 is a side sectional view taken along line A-A in FIG. , 3rd
The drawings are a cross-sectional view taken along line B-B in Fig. 1, Fig. 4 is a perspective view showing a part of an aircraft in which the spanwise blowing device of the present invention is operated, and Fig. 5 The figure is a perspective view showing a part of an aircraft in which the spanwise blowing device of the present invention is not operated, Fig. 6 is a partial plan view of the aircraft showing the collapse of a separated vortex at a high angle of attack, and Fig. 7 is a conventional FIG. 2 is a partial plan view of an aircraft showing separated vortices when the spanwise blowing device of FIG. DESCRIPTION OF SYMBOLS 1... Aircraft, 2... Fuselage, 3... Wing-fuselage blend, 4... Main wing, 5... Fixed wing, 7... Maneuver flap, 8... Air intake, 9... ...Air outlet, 10...Air duct. Applicant's agent Yuki Sato 1 Figure 2

Claims (1)

[Claims] In aircraft with wing-fuselage blends on both sides of the fuselage, wings on the outside of each wing-fuselage blend, and movable leading edge flaps on the leading edges of the wings, air intakes are provided on the underside of the wing-fuselage blends. At the same time, an air outlet is provided on the side surface of the wing fuselage blend that makes sliding contact with the leading edge flap, and the air intake port and the air outlet are communicated through an air duct, and the air outlet is connected to the front side when the leading edge flap is not operated. A spanwise blowing device for an aircraft, characterized in that it is closed by a side end surface of an edge flap and is opened when the leading edge flap is actuated to blow out air in the widthwise direction of the wing.